Missile launcher

ABSTRACT

A missile launcher incorporating therein a novel locking arrangement, ejector means, firing system, energizing means and stray energy monitors. This series of elements function as a new combination providing a more reliable apparatus for securing a missile to an aircraft and, which is capable of, at a predetermined time thereafter, releasing the missile.

United States Patent 1191 Lebovitz Nov. 13, 1973 MISSILE LAUNCHER3,327,629 6/1967 Judd 102/23 3,242,808 3/1966 Nelson 89/l.5 R [75]lnvemor- Bernard 3,444,779 5/1969 Buell et al.... 89/l.8l1 [73] A i TUnited states of America s 3,266,834 8/l966 Lebovitz l 89/1.5 R Xrepresemed by the Secretary of the 3,670,654 6/1972 BlllOt 89/].5 D AirForce, Washington, DC. Primary ExaminerSamuel W. Engle [22] Flled 1972Attorney-Harry A. Herbert, Jr. et al. [21] Appl. No.: 245,061

. [57] ABSTRACT [52] US. Cl 89/1.807, 89/].5 R, 89/l.8l2,

89/1814 A mlssile launcher incorporating therein a novel lock- 51 rm. c1.141: 3/04 arrangement eject means firing system energiz' [58] Field OfSearch 89/1.5 1.811 1.812 mg means and Stray energy monitors- ThisSeries of 89/1 803 L814 1 1 ements function as a new combinationproviding a more reliable apparatus for securing a missile to an [56]References Cited aircraft and, which is capable of, at a predeterminedUNITED STATES PATENTS time thereafter, releasing the missile.

2,826,120 3/1958 Lang et a1. 89/].5 R X 7 Claims, 14 Drawing FiguresPAIENIEU NOV 13 ms SHEET 1 or 5 :FIG 1 PATENTEDNUY 13 ms SHEET UF 5PATENTEDNUY13 i973 SHEET S0? 5 MISSILE LAUNCHER BACKGROUND OF THEINVENTION This invention relates generally to missile launchers, and,more particularly, to a missile launcher which releasably supports themissile under the body of an aircraft.

Various devices have been employed for carrying rockets and missilesunder an aircraft. The missiles have been securely attached to theaircraft during takeoff and flight with the launcher equipped to releasethe missile upon firing thereof. A conventional method of mountingmissiles heretofore employed has been to support the missile in aU-shaped hanger and to hold the missile by spring or other restrainingmeans; Considerable difficulty has been incurred in such an ar rangementto prevent dislodging of the missile from the aircraft when concentrateddeceleration forces are imparted to the aircraft.

Another method imposed in the past to restrain the missile has been theuse of retaining pawls to resist forward motion of the missile and tohold the pawl by a shear-pin of particular strength. The shear-pin isdesigned to hold the missile in place under the concentrateddeceleration forcesimparted to the aircraft in the course of an arrestedlanding. upon the flight deck of an aircraft carrier, for example, andyet not sufficiently large to prevent the firing of the rocketprojectile. Furthermore, launchers of the past were essentiallyunreliable when they incorporated specific firing systems and strayenergy monitors in the system.

SUMMARY OF THEHINVENTION The instant invention sets forth a missilelauncher which overcomes the deficiencies set forth hereinabove. Thelauncher of this invention is lighter in weight, more reliable, simplerin mechanical operation and easier to maintain than the launchers of thepast.

The instant invention sets forth a missilelauncher which is securedbeneath any conventional aircraft. The launcher is of the ejector typewhich is powered by two electrically initiated conventional cartridges.A pair of twin telescoping pistons'are utilized in conjunction with thecartridges in order to eject the missile at approximately twenty feetper second during the firing operation. The energizing means for thelauncher is a gas system in the form of cartridges mounted within thelauncher in a quick disconnect breech which enables the aircraft to berearmed more quickly. The breech houses the two cartridges with theelectrical firing pins located in the cartridge retainers. The breech isinserted within the launcher and a 30 locking turn fixedly secures thebreech and cartridges in place.

The linkage mechanism in the launcher of this invention is designed tocarry the missile throughout the aircraft flight. Launch hooks attach toexisting missile lugs and secure the missile securely to the launcher.The hooks once locked remain positively locked until the missile isarmed or down loaded. This positive lock is accomplished by a solenoidactuated bell crank that locks the hook release. At the time of arming,the energized solenoid unlocks the hook linkage, ready for launch.

A specially designed motor control for the missile is in the form of anumbilical type plug which is capable of energizing the missile and afterlaunch quickly disconnecting from the missile and returning to itsoperative position within the launcher. To insure a quick and safe loadof cartridges and missiles, a stray energy detecting system is alsoincorporated in the missile launcher of this invention.

It is therefore an object of this invention to provide a missilelauncher which reliably secures a missile in place and is capable ofreleasing the missile at a predetermined time.

It is a further object of this invention to provide a missile launcherwhich incorporates therein a preloaded cartridge breech capable of easyinstallation and removal.

It is another object of this invention to provide a missile launcherwhich utilizes a reel-type energizing plug within the launcher.

It is still another object of this invention to provide a missilelauncher containing stray energy monitors.

It is still another object of this invention to provide a missilelauncher which is economical to produce and which utilizes conventional,currently available components that lend themselves to standardproducing manufacturing techniques.

For a better understanding of the present invention together with otherfurther objects thereof, reference is made to the following descriptiontaken in connection with the accompanying drawing and its scope will bepointed out in the'appended claims."

DESCRIPTION OF THE DRAWING FIG. I is a pictorial view of the missilelauncher of this invention illustrating the location of the variouselements thereof;

FIG. 2 is a front view of the missile launcher of this invention withthe missile held securely in place;

FIG. 3a is a partially. cut away side elevational view of the forwardhalf of the missile launcher of this invention, shown partly in crosssection;

FIG. 3b is a partially cut away side elevational view of the rear halfof the missile launcher of this invention, shown partly in crosssection;

FIG. 4 is a side elevational view of a portion of the missile launcherof this invention showing the linkage mechanism and launcher hooks inthe locked position;

FIGS is a side elevational view of the linkage mechanism of the missilelauncher of this invention;

FIG. 6 is a side elevational view of a portion of the missile launcherof this invention-showing the linkage mechanism and launcher hooksthereof in the unlocked position;

FIG. 7 is a side elevational view of the missile motor plug returnassembly of the missile launcher of this invention, with phantom linesshowing the plug in the extended position;

FIG. 8 is a side elevational view of a portion of the missile launcherof this invention showing the location of the quick disconnect breech;

FIG. 9 is a side elevational view of the cartridges within the breech ofthe missile launcher of this invention;

FIG. 10 is a bottom view of the quick disconnect breech of the missilelauncher of this invention;

FIG. 1'] is a side elevational view of a portion of the missile launcherof this invention showing the location of the stray energy monitors;

FIG. 12 is a side elevational view of a stray energy monitor of themissile launcher of this invention; and

FIG. 13 is a schematic diagram of the circuitry of the stray energymonitors of the missile launcher of this invention.

DETAILED DESCRIPTION OF THE PREFERRED I EMBODIMENT Reference is now madeto FIG. 1 of the drawing which discloses in pictorial fashion themissile launcher of this invention supporting securely in position aconventional missile 12. The missile 12 has a yoke 14 with lug 15attached thereto (FIG. 2) at one end thereof and launcher lugs 16 at theother end thereof. Launcher 10 is made up of a launcher body 11 whichincorporates therein a linkage mechanism 22 to operate at least one pairof launcher hooks 24 and 26, in a manner to be described in detailhereinbelow, for engaging lugs 15 and 16, thereby holding missile 12securely in place as shown in FIGS. 1 and 2. Still referring to FIG. 1of the drawing the launcher body '11 has a pair of twin telescopingpistons 18 located within housings 19 at either end thereof utilized inejecting the missilev 12 during the firing operation. A gas systemsupplies the energy source for actuating these pistons 18 and is in theform of conventional electrically initiated cartridges located within aquick disconnect breech 20 in the forward part of launcher 10.

Reference is now made to FIGS. 2, 3a and b, and FIG. 4 of the drawingwhich show the linkage mechanism 22 utilized to operate hooks 24 and 26.FIGS. 3a, 3b and 4 show that linkage mechanism 22 is operably connectedto the pair of launcher hooks 24 and 26 which are pivotally mounted tobody 11 by pins 28 and 30, respectively. For additional support ofmissile 12 hooks 24 and 26 may be formed in duplicate also supported bypins 28 and 30 and operated by linkage mechanism 22 in the manner shownin' FIGS; 1 and 2. For simplicity, however, in the description of thelauncher 10 this invention reference will be made to only one set ofhooks 24 and 26 with any further number of hooks to be mounted in anidentical manner.

Referring to FIGS. 3a and 5, a safety solenoid 32 allows .for therelease of linkage mechanism 22 of launcher 10 in a manner describedbelow. The linkage mechanism 22 has a bellcrank 34 pivotally mounted onpin 35 within launcher body 11. Bellcrank 34 has attached thereto at oneend an elongated link 36 pivotally secured thereto at 38 and at theother end elongated link 40 pivotally secured thereto at 42. Links 36and 40 are then secured to hooks 24 and 26, respectively, by pins 44 and46 as shown in FIGS. 3a, 3b and 4 of the drawing.

A two bar linkage 48, made up of bars 52 and 54, shown in FIGS. 3a and 5is pivotally secured to body 11 by pin 50, and to bellcrank 34 by pin58, with the bars 52 and 54 joined together at 55 by any suitablesecuring means. In the locked position shown in FIG. 4 a safety pin 56fixedly attaches two bar linkage 48 to body 11 and thereby preventsmovement of mechanism 22. Referring once again to FIGS. 3a and 5solenoid 32 has an actuator 60 connected thereto. Actuator 60 haspivotally secured at one end thereof at 61 a hook shaped element 62.Element 62 is further pivotally secured within launcher body 11 by pin64, and, is operably secured to the joining point 55 of two bar linkage48 by element 66. The hook shaped element 62 engages an outstandingelement 68 on bellcrank 34 during the locked position of launcher 10shown in FIGS. 30 and 4.

A slave piston 70 (FIGS. 3a and 5) is mounted within a housing 72 in aconventional manner and is located adjacent the joining point 55 of twobar linkage 48. This piston 70 receives its actuating force from the gasreleased from the cartridges within breech 20 by a system to beexplained in detail hereinbelow.

Reference is now made to FIGS. 4, 5 and 6 which show the linkagemechanism 22 operated from the locked position of FIG. 4 to the unlockedposition of FIG. 6. Upon the removal of safety pin 56 and upon theenergizing of solenoid 32, hook element 62 is withdrawn to the positionshown in FIG. 6. Simultaneously with the above action piston 70 movesagainst the joining point 55 of two bar linkage 48 causing the movementof two bar linkage 48 to the position shown in FIG. 6. This actionproduces movement of bellcrank 34 about pivot point 36 which thenretracts elongated links 36 and 40 causing the pivotal movement of hooks24 and 26 respectively, thereby releasing the missile 12 for operationthereof, further assisted by the action of pistons 18. v

The firing system for missile 12 incorporated within launcher 10 of thisinvention is best shown in FIGS. 3a and 7 of the drawing. This system 80utilizes a missile motor plug 82 electrically connected by a coiled wire84 and launcher plug 86 to any conventional firing source (not shown).Plug 82 is shown in its retracted position in FIGS. 3a and 7 and, in itsextended position in phantom in FIG. 7. During operation plug 82 isinserted within plug insert 83 of missile 12 (FIG. 3a) while missile 12is supported by launcher 10. A spring reel housing 88 (FIG. 7) enclosesa pair of spring loaded pulleys 90 (FIG. 3a). A cable 92 is secured atone end to pulleys 90 and at the other to plug 82. Upon the release ofmissile l2, plug 82 extends beyond the missile launcher 10 as shown inFIG. 7 allowing the firing of missile 12 to take place. Upon furtherejection of missile 12 by pistons 18, plug 82 then disengages frommissile l2 and returns tolauncher 10 to its retracted position as shownin both FIGS. 3a and 7.

Supplying the gas source for the operation of the linkage mechanism 22as well as the pistons 18 is a pair of conventional gas cartridges 96located within a quick disconnect breech 20 shown in FIGS. 1, 3a, and 8through 10. Quick disconnect breech 20 enables the aircraft utilizinglauncher 10 of this invention to be rearmed more quickly. The breech 20houses the pair of cartridges 96 as shown in FIG. 9 with an electricalfiring plug 98 located in the cartridge retainers. Insertion of thebreech 20 within the launcher body 11 is shown in exaggerated fashion inFIG. 8 of the drawing and a 30 locking turn as shown in FIG. 10 installsthe breech 20 within the body 11. This breech 20 is held securely inplace by any conventional securing means such as a ball detent 98 whichabuts lug 100 on breech 20 as shown in FIG. 10.

FIGS. 1, 3a, and 9 more clearly show gas ports 102 and lines' 104 whichare utilized tosupply the gas from cartridges 96 to piston 70 foractuating linkage mechanism 22'as well as piston 18 for ejection ofmissile 10. Complete detail of the gas system is not shown since anyconventional use of valves, lines and the like may be used with thequick disconnect breech arrangement 20 of this invention.

To insure a quick and safe loading of cartridges 96 and missile 12, aconventional stray energy detecting system or monitors 110 shown inFIGS. 3a and 11 through 13 has been incorporated in the missile launcherfiring circuits. The stray energy monitors 110 are switched into and outof operation by the circuitry 112 shown in FIG. 13 which depends uponsafety pin 56 shown in both FIGS. 3a, 11 and 13 for its operation.Insertion of pin 56 not only looks two bar linkage 48 securely inposition in order to prevent inadvertent actuation of the linkagemechanism 22 (FIG. 3a) but also allows stray energy monitors 110 to actupon the detection of any stray energy in the circuits. Any stray energycauses the actuation of pins 114 within any one of a plurality of thestray energy monitors 110. Pins 114 protrude into view (as shown in FIG.12) so any personnel by sight or touch inspection can determine whetherthe aircraft and/or launcher should be set aside for further testing inorder to isolate the source of the stray energy. If no stray energyisdetected, removal of safety pin 56 places linkage mechanism 22 inreadiness for operation and as seen from FIG. 13 transfers the firingcircuits back to the normal operation.

MODE OF OPERATION The missile launcher of this invention operates in thefollowing manner:

The quick disconnect breech and safety pin 56 are inserted into thelauncher body 11. The missile 12 as shown in FIG. 1 of the drawing islocked into position beneath launcher 10 by means of a plurality oflauncher hooks 24 and 26 and the positive lock oflinkage mechanism 22.Before take-off of the aircraft associated with the launcher 10 of thisinvention, inspectors check the stray energy monitors 110 for any sourceof stray energy. If the check is satisfactory, safety pin 56 iswithdrawn from two bar linkage 48 and the missile launcher 10 is readyfor the release and firing of missile 12.

At a predetermined time the solenoid 32 is energized unlocking thelinkage mechanism 22. When the missile 12 is to be launched, actuationof cartridges 96 in any conventional manner such as by electrical plug98 produces a gas which forces piston 70 into the position shown in FIG.6 of the drawing causing the inward movement of two bar linkage 48 andthe release of hooks 24 and 26 from lugs 15 and 16. The missile 12 isthereby released from its position beneath launcher l0 and under theaction of pistons 18 is expelled from beneath the aircraft. Missile 12is fired in any conventional manner through the use of the missile motorplug 82. With missile 12 a predetermined distance from launcher 10, plug82 will disconnect from missile 12 and return to its original positionas shown in FIG. 7. The missile 12 now operates under its own power.

The launcher 10 of this invention has eliminated any unnecessary timeconsuming methods and procedures found in the prior art. For example, nolonger will the ground crew have to remove both cartridge retainers inorder to reload the launcher 10 since this operation is now accomplishedwith a preloaded breech 20 that is installed and locked with a simple 30twist. No longer will it be necessary to use circuit testers to analyzethe firing circuit for stray voltage; now the stray energy monitors 110will advise the inspectors at a glance. Furthermore, the books whichheretofore were manually latched to the missile lugs are now closed andsafety locked ready for release by linkage mechanism 22. Also plug 82 isreadily returned to the launcher 10 by means of the motor plug returnassembly 80.

Although this invention has been described with reference to aparticular embodiment it will be understood to those skilled in the artthat this invention is also capable of a variety of alternateembodiments within the spirit and scope of the appended claims.

I claim:

1. A missile launcher comprising an elongated body, means mounted withinsaid launcher body for releasably securing a missile thereto, a linkagemechanism operably associated with said missile securing means forpositively locking and unlocking said missile securing means, meansretractably secured within said launcher body for firing said missile,means located within said launcher body for detecting stray energy,ejector means located within said launcher body for ejecting saidmissile, energizing means releasably secured within said launcher bodyfor actuating said link age mechanism and said ejector means, saidenergizing means comprising a plurality of gas cartridges, saidcartridges being located within a quick disconnect breech,

said breech being mounted within an opening in said launcher body, and alocking means located adjacent said opening whereby a 30 locking turn ofsaid breech securely holds said breech in position, and a solenoidoperably connected to said linkage mechanism, in one position saidsolenoid prevents movement of said linkage mechanism while in a secondposition allows said linkage mechanism to move under the influence ofsaid energizing means, whereby upon the failure to detect stray energyand at a predetermined time, said missile securing means releases saidmissile, said missile is fired and said missile is ejected under theaction of said ejector means.

2. A missile launcher as defined in claim 1 wherein said retractablefiring means comprises a plug, at least one spring loaded pulley mountedwithin said launcher body, a cable secured at one end thereof to saidpulley and at the other end thereof to said plug, whereby saidplug'initially engages said missile, withdraws from said launcher bodyupon ejection of said missile, disengages from said missile at apredetermined distance from said launcher, and subsequently retractsinto said launcher body.

3. A missile launcher as defined] in claim 1 wherein said missilesecuring means comprises at least one pair of hooks pivotally mountedwithin said launcher body, each of said hooks being connected to saidlinkage mechanism by an elongated link, whereby movement of said linkagemechanism causes movement of said hooks to the locked or unlockedposition.

4. A missile launcher as defined in claim 3 wherein said linkagemechanism comprises a bellcrank pivotally mounted within said launcherbody, one end of said bellcrank being connected to one of said elongatedlinks, the other end of said bellcrank being connected to the other ofsaid elongated links, a two bar linkage having one link thereofpivotally secured to said launcher body while the other link thereof ispivotally secured to said bellcrank, an actuator located adjacent thejoining point of said two bar linkage, and said actuator being operablyconnected to said energizing means whereby said actuator upon actuationby said energizing means moves said two bar linkage, the movement ofsaid twobar linkage causing a pivotal movement of said bellcrank, whichin turn retracts said elongated links causing unlocking of said hooks.

5. A missile launcher as definedin claim 4 wherein said retractablefiring means comprises a plug, a spring reel housing located within saidlauncher body, at least one spring loaded pulley within said housing,and a cable secured at one end thereof to said pulley and at the otherend thereof to said plug, whereby said plug initially engages saidmissile, withdraws from said launcher body upon ejection of saidmissile, disengages from said missile at a predetermined distance fromsaid launcher and subsequently retracts into said launcher body.

tector.

1. A missile launcher comprising an elongated body, means mounted withinsaid launcher body for releasably securing a missile thereto, a linkagemechanism operably associated with said missile securing means forpositively locking and unlocking said missile securing means, meansretractably secured within said launcher body for firing said missile,means located within said launcher body for detecting stray energy,ejector means located within said launcher body for ejecting saidmissile, energizing means releasably secured within said launcher bodyfor actuating said linkage mechanism and said ejector means, saidenergizing means comprising a plurality of gas cartridges, saidcartridges being located within a quick disconnect breech, said breechbeing mounted within an opening in said launcher body, and a lockingmeans located adjacent said opening whereby a 30* locking turn of saidbreech securely holds said breech in position, and a solenoid operablyconnected to said linkage mechanism, in one position said solenoidprevents movement of said linkage mechanism while in a second positionallows said linkage mechanism to move under the influence of saidenergizing means, whereby upon the failure to detect stray energy and ata predetermined time, said missile securing means releases said missile,said missile is fired and said missile is ejected under the action ofsaid ejector means.
 2. A missile launcher as defined in claim 1 whereinsaid retractable firing means comprises a plug, at least one springloaded pulley mounted within said launcher body, a cable secured at oneend thereof to said pulley and at the other end thereof to said plug,whereby said plug iniTially engages said missile, withdraws from saidlauncher body upon ejection of said missile, disengages from saidmissile at a predetermined distance from said launcher, and subsequentlyretracts into said launcher body.
 3. A missile launcher as defined inclaim 1 wherein said missile securing means comprises at least one pairof hooks pivotally mounted within said launcher body, each of said hooksbeing connected to said linkage mechanism by an elongated link, wherebymovement of said linkage mechanism causes movement of said hooks to thelocked or unlocked position.
 4. A missile launcher as defined in claim 3wherein said linkage mechanism comprises a bellcrank pivotally mountedwithin said launcher body, one end of said bellcrank being connected toone of said elongated links, the other end of said bellcrank beingconnected to the other of said elongated links, a two bar linkage havingone link thereof pivotally secured to said launcher body while the otherlink thereof is pivotally secured to said bellcrank, an actuator locatedadjacent the joining point of said two bar linkage, and said actuatorbeing operably connected to said energizing means whereby said actuatorupon actuation by said energizing means moves said two bar linkage, themovement of said two bar linkage causing a pivotal movement of saidbellcrank, which in turn retracts said elongated links causing unlockingof said hooks.
 5. A missile launcher as defined in claim 4 wherein saidretractable firing means comprises a plug, a spring reel housing locatedwithin said launcher body, at least one spring loaded pulley within saidhousing, and a cable secured at one end thereof to said pulley and atthe other end thereof to said plug, whereby said plug initially engagessaid missile, withdraws from said launcher body upon ejection of saidmissile, disengages from said missile at a predetermined distance fromsaid launcher and subsequently retracts into said launcher body.
 6. Amissile launcher as defined in claim 5 wherein said ejector meanscomprises at least one gas operated piston.
 7. A missile launcher asdefined in claim 9 further comprising a safety pin operably connected tothe joining point of said two bars of said two bar linkage and saidstray energy detector, whereby with said safety pin in position said twobar linkage is prevented from moving and said stray energy detector isoperable, while extraction of said safety pin allows movement of saidtwo bar linkage and disconnection of said stray energy detector.